EP2514673A1 - Phares combinés de roulage au sol et d'atterrissage montés sur la surface de commande - Google Patents

Phares combinés de roulage au sol et d'atterrissage montés sur la surface de commande Download PDF

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Publication number
EP2514673A1
EP2514673A1 EP20120163510 EP12163510A EP2514673A1 EP 2514673 A1 EP2514673 A1 EP 2514673A1 EP 20120163510 EP20120163510 EP 20120163510 EP 12163510 A EP12163510 A EP 12163510A EP 2514673 A1 EP2514673 A1 EP 2514673A1
Authority
EP
European Patent Office
Prior art keywords
light
control surface
light assembly
leds
housing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP20120163510
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German (de)
English (en)
Other versions
EP2514673B1 (fr
Inventor
David Barnett
Jeffrey M. Singer
Timothy C. Martin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Honeywell International Inc
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Honeywell International Inc
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Filing date
Publication date
Application filed by Honeywell International Inc filed Critical Honeywell International Inc
Publication of EP2514673A1 publication Critical patent/EP2514673A1/fr
Application granted granted Critical
Publication of EP2514673B1 publication Critical patent/EP2514673B1/fr
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/02—Arrangements or adaptations of signal or lighting devices
    • B64D47/06—Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/02—Arrangements or adaptations of signal or lighting devices
    • B64D47/04—Arrangements or adaptations of signal or lighting devices the lighting devices being primarily intended to illuminate the way ahead
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D2203/00—Aircraft or airfield lights using LEDs

Definitions

  • HID lamps have been substituted for traditional PAR-46- and PAR-64-sized lamps. While the HID lamps are somewhat smaller for a given output, than the older PAR lamps, the packaging requirements are similar and have required placement within the traditional aircraft locations.
  • Landing lights are used for added conspicuity whenever the aircraft is below a defined altitude. This is true both out-bound and inbound, as well as in an orbiting pattern. This defined altitude ranges from 18,000 to 10,000, feet based on local requirements. In many cases an aircraft is operating below the altitude that requires switching on a landing light yet prior to lowering the landing gear. Lights mounted in the wing root/strakelet area or retractable lights are normally used before the landing gear is lowered.
  • the present invention provides an array of solid-state light-emitting diodes (LEDs) in the moving control surface mounted on the leading edge of the wing.
  • LEDs solid-state light-emitting diodes
  • An array of LEDs is fitted to one or more areas of a wing's forward control surface.
  • the light intensity is limited only by the surface area devoted to the array.
  • the protective lens and thermal management solution limit the array size by the resultant weight of the assembly.
  • forward-facing lenses are typically glass. The rather high density of glass makes the lens a significant portion of the light assembly's weight.
  • the current state-of-the -art LED products are a balance between how hard the devices are driven and the thermal efficiency. LEDs are more efficient as the drive current drops. There is a best-case point at which the light output and the thermal losses with the resultant heat dissipation features are reached.
  • the light assembly is fitted to the inboard slat only.
  • This inner slat is constructed of aluminum materials or a thermally conductive composite material to allow the aircraft structure to buffer the temperature rise in the LEDs and dissipate the heat into the air flowing over the wing.
  • the remainder of the wing surfaces are unaffected and can be constructed of metallic or nonthermally conductive composite material, as desired by the airframe designer.
  • Adding the light assembly's weight to the slat assembly typically does not require changes to the control surface mechanical systems.
  • the added weight of the light assembly is typically insignificant in relationship to the forces applied from airflow at a typical maximum 250 knots airspeed for deployment.
  • FIGURES 1 and 2 illustrate landing and taxi lights mounted on aircraft in accordance with the prior art
  • FIGURE 3 illustrates a side view of an aircraft having a movable control surface formed in accordance with an embodiment of the present invention
  • FIGURE 4 illustrates a perspective view of a movable control surface formed in accordance with an embodiment of the present invention
  • FIGURE 5 illustrates an exploded view of a lighting assembly for mounting within a movable control surface
  • FIGURE 6 illustrates a cross-sectional view of the lighting assembly shown in FIGURE 5 ;
  • FIGURE 7 illustrates a light system formed in accordance with an embodiment of the present invention
  • FIGURE 8 illustrates an exploded view of the light assembly shown in FIGURE 7 ;
  • FIGURE 9 illustrates a light system formed in accordance with an embodiment of the present invention.
  • FIGURE 10 illustrates a perspective view of an aircraft in a cruise mode of flight
  • FIGURE 11 illustrates an aircraft in a landing mode of flight.
  • an aircraft 14 is shown in a landing-mode configuration with gear down and flaps and slats 18 deployed on a wing 16.
  • One or more light-emitting diode (LED) light assemblies are embedded into a movable control surface.
  • the slat 18 is the movable control surface in this example.
  • the slat 18 is a full leading-edge slat.
  • the slat 18 includes one or more light-emitting diode (LED) light assemblies 20.
  • the light assemblies 20 that are included within the slat 18 are a fixed-mounted assembly, which casts light only in a set angular pattern from the slat 18, and/or are a variable-pitch light assembly that can rotate the outputted spectrum of light from the slat 18.
  • the fixed light assembly is preferably one that would be used in a slat that does not rotate between a stowed and a deployed position. In other words, as the slat deploys, the slat does not rotate greater than a threshold amount relative to the wing.
  • the variable-pitch LED light assembly is used in a slat that does rotate when deployed. In another embodiment, the variable-pitch LED light assembly is used if one desires manual or automatic control of direction of the light produced by the light assembly from the slat, regardless of slat or wing orientation.
  • FIGURE 4 illustrates a perspective view of a slat 18-1 with two light assemblies 20-1 mounted therein.
  • the surface of the light assemblies 20-1 is mounted flush with the surface of the slat 18-1.
  • the depth the light assemblies 20-1 is not large enough to conflict with the traditional slat hardware used for stowing and deploying the slat 18-1.
  • FIGURE 5 a fixed light assembly 20-2 that includes an LED enclosure 24, an LED strip 26, a housing 28, and a lens assembly 30.
  • the LED strip 26 mounts within the LED enclosure 24.
  • the LED enclosure 24 and the lens assembly 30 mount to the housing 28.
  • the housing 28 is secured within a movable control surface such that the lens assembly 30 is flush with the surface of the movable control surface.
  • Traditional fasteners and epoxies are used for attaching the components of the fixed light assembly 20-2 and for attaching the fixed light assembly 20-2 to the movable control surface.
  • FIGURE 6 illustrates a cross-sectional side view of the light assembly 20-2 of FIGURE 5 .
  • the LED strip 26 mounts to the LED enclosure 24.
  • the LED strip 26 and/or the LED enclosure 24 includes electrical traces for electrically connecting LEDs 36 that are mounted on the LED strip 26 to externally attached cables.
  • Surrounding one or more of the LEDs 36 on the LED strip 26 are reflectors 38.
  • the reflectors 38 are formed of or include a highly reflective material on at least the inner walls of the reflector 38.
  • the LED enclosure 24 then mounts to the housing 28.
  • the housing 28 receives the lens assembly 30, such that a seal exists between the lens assembly 30 and the housing 28.
  • FIGURE 7 illustrates a side view of a light 58 that has the ability to rotate relative to the control surface on which it is mounted.
  • the light 58 includes a rotary mount base 60 that is fixedly attached to the control surface.
  • the light 58 also includes a light strip 62 that includes a plurality of LEDs (or comparable light sources) and reflectors mounted on one side.
  • the light strip 62 is mounted to a rotary housing 66, which is secured within the rotary mount base 60 by a retainer block 64.
  • a mechanical linkage 68 is attached at one end to the rotary housing 66 and at another end to a gear assembly 70 which attaches to a slat extension linkage (e.g., guide rods, struts, cams or similar components) 72.
  • the aiming direction of the light is a function of the position of the slat with the aim fixed in relationship to the attachment orientation at the stage of deployment or retraction of the slat.
  • FIGURE 8 a rotating light assembly 20-3 (such as that used in FIGURE 7 ) that includes an LED enclosure 80, a rotating assembly 82, an LED strip 84, a housing 86, and a lens assembly 88.
  • the LED strip 84 mounts to the rotating assembly 82 and the rotating assembly 82 mounts within the LED enclosure 80.
  • the LED enclosure 80 and the lens assembly 88 mount to the housing 86.
  • the housing 86 is secured within a movable control surface such that the lens assembly 88 is flush with the surface of the movable control surface.
  • Traditional fasteners and epoxies are used for attaching the components of the fixed light assembly 20-3 and for attaching the fixed light assembly 20-3 to the movable control surface.
  • the aim of the light produced by the light system is independent of the position of the respective control surface or aircraft attitude.
  • a rotary light base is coupled to a drive motor or positioner that moves to generate a desired aim for the flight phase.
  • the aim can be determined by local control (e.g., firmware or attitude sensor) or incorporated into a flight management system (FMS) that responds to automated take-off and landing sequence of events.
  • FMS flight management system
  • a processor provides a position signal to a motor based on a control signal received at the processor.
  • the control signal may be one generated at a cockpit user interface device (i.e., a light position controller) or includes information related to flight of the aircraft, position of the slat in which the rotatable light assembly is mounted, and/or angle of attack of the aircraft.
  • the processor executes logic, stored in local memory, for interpreting the received control signal and generating the position signal accordingly. For example, if the processor first receives a 2° nose-up angle-of-attack value, the position signal generated by the processor is a -2° nose-down value. Then, when the aircraft transitions to the landing configuration and the angle-of-attack value goes to 8° nose up, the position signal generated by the processor is an -8° nose-down value, thus compensating for the rotation of the aircraft.
  • the processor can compensate for other factors in order to keep the pattern of light generated by the LEDs at an optimum location.
  • the motor used in this embodiment may be a direct drive stepper motor, a gear driven stepper motor if rotation torque is high enough to necessitate the weight of a gear case, or a servo-drive and encoder.
  • the servo-drive and encoder would be more likely used in an analog control system with an attitude target rather than a FMS controlled system.
  • a common positioner with connecting linkage or independent positioners is used.
  • Independent positioners that are in signal communication with a flight management system (FMS) may be used thus allowing the FMS to increase the vertical light pattern for a portion of the flight profile.
  • FMS flight management system
  • one array of light assemblies in a slat is aimed a few degrees higher or lower than another array of light assemblies in the same slat. This reduces the peak intensity but increases the vertical pattern. This might be benefitial during a flare to touchdown without requiring dynamic aim control from the FMS. This dynamic aiming allows maximum intensity at a defined location in relationship to a flight deck.
  • FIGURE 9 illustrates a rotating light system 98.
  • the rotating light system 98 includes an LED enclosure 100 that is configured to receive a rotary actuator 102.
  • Mounted to the rotary actuator 102 is an LED strip 103 that includes a plurality of LEDs and associated reflectors.
  • the LED enclosure 100 is then received by a housing 106 with a lens assembly 108 mounted thereto.
  • the rotary actuator 102 is shown in a slightly pitched-up attitude.
  • a controller 110 is attached to the rotary actuator 102.
  • the controller 110 receives input signals comparable to those received by the processor 72, described above with regard to FIGURE 7 .
  • the controller 110 responds similarly to the rotary actuator 102, except that the output signal produced by the controller 110 is conducive for the rotary actuator 102, versus the motor 70.
  • the internal structure shown in the rotary actuator 102 is part of a thermal management system.
  • a rotary tube is filled with an organic phase change material (PCM) to store the thermal energy during operation.
  • PCM organic phase change material
  • Internal fins are used to conduct heat into the poor thermally conductive PCM.
  • FIGURE 10 illustrates a large cargo aircraft 120 in a cruise mode of flight below a certain altitude that requires the aircraft 120 to be illuminating landing lights.
  • the aircraft 120 includes one or more LED light assemblies included within one or more of the leading-edge slats.
  • the illumination pattern produced by the LED light assembly in the slats, when the aircraft is in the clean cruise mode of flight, is at a first range, as shown by the dashed lines extending from the leading edge of the wing of the aircraft 120.
  • FIGURE 11 shows the aircraft 120 in a landing mode of flight with the gear down and slats deployed.
  • the light assembly included within the slat is rotated in order to maintain the desired illumination pattern.
  • nearly any desirable lower and upper angle-of-attack value for the illumination can be obtained.
  • a fixed-mounted LED assembly may be used in one or more of the slats of the aircraft 120.
  • multiple LED assemblies are located on one or more slats on a wing.
  • LED light assemblies may be included in other movable control surfaces, such as the flaps, canards, etc.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Non-Portable Lighting Devices Or Systems Thereof (AREA)
  • Arrangement Of Elements, Cooling, Sealing, Or The Like Of Lighting Devices (AREA)
EP20120163510 2011-04-19 2012-04-09 Phares combinés de roulage au sol et d'atterrissage montés sur la surface de commande Active EP2514673B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/090,013 US8337059B2 (en) 2011-04-19 2011-04-19 Control-surface-mounted landing and taxi lights

Publications (2)

Publication Number Publication Date
EP2514673A1 true EP2514673A1 (fr) 2012-10-24
EP2514673B1 EP2514673B1 (fr) 2015-05-20

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US (1) US8337059B2 (fr)
EP (1) EP2514673B1 (fr)
CN (1) CN103101630B (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3013331A1 (fr) * 2013-11-15 2015-05-22 Zodiac Aero Electric Systeme optique d'eclairage pour aeronef
EP3335997A1 (fr) * 2016-12-18 2018-06-20 Goodrich Lighting Systems GmbH Procédé de fonctionnement d'un système de projecteur d'aéronef, système de projecteur d'aéronef et aéronef comprenant ledit dispositif
EP3808662A1 (fr) * 2019-10-15 2021-04-21 Goodrich Lighting Systems, Inc. Ensemble d'éclairage d'aéronef à visée réglable

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US9091401B2 (en) * 2012-11-21 2015-07-28 Milwaukee Electric Tool Corporation Work light
US9386665B2 (en) 2013-03-14 2016-07-05 Honeywell International Inc. System for integrated lighting control, configuration, and metric tracking from multiple locations
EP2833059B1 (fr) * 2013-08-01 2016-06-15 Goodrich Lighting Systems GmbH Unité de lumière à DEL d'aéronef
CN104633536B (zh) * 2013-11-14 2018-11-16 上海航空电器有限公司 一种与机翼共形的大曲面编队灯
KR101553681B1 (ko) 2014-02-12 2015-10-16 (주)에이엔에이치스트럭쳐 항공기용 스트로브 라이트 조립체
USD742052S1 (en) 2014-02-26 2015-10-27 Milwaukee Electric Tool Corporation Lantern
USD792617S1 (en) * 2014-07-18 2017-07-18 Icon Aircraft, Inc. Aircraft wingtip position light
US9650154B2 (en) * 2014-12-05 2017-05-16 Gulfstream Aerospace Corporation Aircraft landing gear assemblies with non-rotating light element clusters
EP3106392B1 (fr) 2015-06-19 2018-06-06 Goodrich Lighting Systems GmbH Unite lumineuse d'eclairage d'un stabilisateur vertical d'un aeronef et procede de fonctionnement d'un stabilisateur vertical d'une unite lumineuse d'eclairage d'un stabilisateur vertical d'un aeronef
ES2769642T3 (es) * 2015-09-10 2020-06-26 Goodrich Lighting Systems Gmbh Unidad de iluminación exterior dinámica de aeronave y método para operar una unidad de iluminación exterior dinámica de aeronave
US9643736B1 (en) 2016-04-14 2017-05-09 Goodrich Corporation Systems and methods for landing lights
US9856035B1 (en) * 2016-06-09 2018-01-02 Goodrich Corporation Systems and methods for dynamic light control
FR3057546B1 (fr) * 2016-10-19 2021-12-31 Zodiac Aero Electric Projecteur de piste multifonctions a commutation de fonctions statique pour aeronef
US10322818B2 (en) 2016-11-18 2019-06-18 Goodrich Lighting Systems, Inc. Multi-beam light
US11691757B2 (en) 2021-08-23 2023-07-04 Nathan Howard Calvin Aircraft exterior lighting multi-emitter array for variable beam profile

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EP1138593A1 (fr) * 2000-03-31 2001-10-04 Hella KG Hueck & Co. Phare pour avions
DE10159134A1 (de) * 2001-11-17 2003-06-05 Christian Josef Krahe Scheinwerferanordnung für ein Flugzeug
US7324016B1 (en) * 2005-11-22 2008-01-29 The United States Of America As Represented By The Secretary Of The Navy Navigational indicating system for rotary wing aircraft
US20080137353A1 (en) * 2006-12-08 2008-06-12 Larsen Ty A Multi-mode exterior lighting architectures for aircraft

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3013331A1 (fr) * 2013-11-15 2015-05-22 Zodiac Aero Electric Systeme optique d'eclairage pour aeronef
FR3036099A1 (fr) * 2013-11-15 2016-11-18 Zodiac Aero Electric Systeme optique d'eclairage pour aeronef
US10494120B2 (en) 2013-11-15 2019-12-03 Zodiac Aero Electric Optical lighting system for an aircraft
EP3335997A1 (fr) * 2016-12-18 2018-06-20 Goodrich Lighting Systems GmbH Procédé de fonctionnement d'un système de projecteur d'aéronef, système de projecteur d'aéronef et aéronef comprenant ledit dispositif
US10266281B2 (en) 2016-12-18 2019-04-23 Goodrich Lighting Systems Gmbh Method of operating an aircraft headlight system, aircraft headlight system, and aircraft comprising the same
EP3808662A1 (fr) * 2019-10-15 2021-04-21 Goodrich Lighting Systems, Inc. Ensemble d'éclairage d'aéronef à visée réglable

Also Published As

Publication number Publication date
EP2514673B1 (fr) 2015-05-20
CN103101630A (zh) 2013-05-15
US8337059B2 (en) 2012-12-25
CN103101630B (zh) 2017-04-12
US20120268959A1 (en) 2012-10-25

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